WO2023123732A1 - Loading device and method for multi-point hoisting static testing of spacecraft cabin body - Google Patents
Loading device and method for multi-point hoisting static testing of spacecraft cabin body Download PDFInfo
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Abstract
A loading device and method for multi-point hoisting static testing of a spacecraft cabin body. The device comprises: a force bearing ground rail (1), a force bearing support (2), inclined supports (3), loading force bearing beams (4) and a loading mechanism (5), wherein the force bearing support (2) is mounted on the force bearing ground rail (1); the force bearing support (2) comprises vertical support beams (21) and horizontal force bearing beams (22); the force bearing support (2) builds a cabin body testing space to fit with a cabin body structure; the inclined supports (3) are mounted on side faces of the bottom of the force bearing support (2); a plurality of loading force bearing beams (4) are mounted and fixed above the force bearing support (2); and the loading mechanism (5) is mounted on the loading force bearing beam (4). The device is used to perform hoisting static testing on hoisting interfaces of a large cabin body, so as to assess the structural characteristics and bearing capacity of hoisting point positions, and ensure the stability of a spacecraft during hoisting and transfer processes; transverse and longitudinal loads can be applied to different hoisting point positions to simulate stress under different conditions; and the device can meet the loading requirements of a plurality of hoisting points.
Description
本发明涉及航天器力学试验技术领域，尤其是提供了一种航天器舱体多点起吊静力试验加载装置及方法。 The invention relates to the technical field of spacecraft mechanics tests, and in particular provides a multi-point hoisting static test loading device and method for a spacecraft cabin.
对于空间站大型舱体，在其结构板或外部结构相邻位置上往往设置多处起吊接口。在对舱体进行考核时，需要对吊接口进行起吊静力试验，主要是对吊点位置的结构性能进行测试，考核吊点位置结构的合理性及承载能力，保证航天器在起吊、转运过程中的可靠性和稳定性。试验时需针对不同阶段的安装要求，在不同吊点位置，施加横向、纵向载荷，模拟大型舱体不同阶段的起吊、运输情况。For the large cabin of the space station, multiple lifting interfaces are often provided on the adjacent positions of the structural plate or the external structure. When evaluating the cabin body, it is necessary to carry out a static lifting test on the lifting interface, mainly to test the structural performance of the lifting point position, to assess the rationality and carrying capacity of the structure at the lifting point position, and to ensure that the spacecraft is in the process of lifting and transferring. reliability and stability in . During the test, according to the installation requirements of different stages, lateral and longitudinal loads are applied at different lifting point positions to simulate the lifting and transportation conditions of large cabins at different stages.
现有技术中，对于大型舱体起吊静力试验，会在每个吊点位置采用安装单独加载工装，通过安装单独的横、纵向承力支架和配套的横、纵向加载装置，将载荷传递到起吊吊点位置，以此来模拟舱体安装各结构时，起吊、转运过程中所受的横向和纵向载荷。而对于设置有多组吊点的舱体结构，若继续采用原有加载方式，来满足对不同阶段的起吊运输，必然会增加试验安装的工作量及安装的风险。 In the prior art, for the static test of large-scale cabin lifting, a separate loading tool will be installed at each lifting point, and the load will be transferred to the The position of the lifting point is used to simulate the lateral and longitudinal loads in the process of lifting and transferring when the cabin body is installed with various structures. As for the cabin structure with multiple sets of lifting points, if the original loading method is continued to meet the lifting and transportation at different stages, the workload of test installation and the risk of installation will inevitably increase.
为此需要对现有的起吊静力试验加载装置及方法做进一步的改进，从而满足航天器大型舱体起吊加载点数量多的情况，为考核不同安装阶段的要求，设计一种承载稳定、结构简单、安装、调节方便的加载装置，实现航天器大型舱体起吊工况的考核。Therefore, it is necessary to further improve the existing lifting static test loading device and method, so as to meet the large number of loading points for the lifting of a large spacecraft cabin, and to design a load-bearing stable, structural The loading device is simple, easy to install and adjust, and realizes the assessment of the lifting conditions of the large cabin of the spacecraft.
为了进行大型舱体起吊静力试验，保证试验加载装置的承载稳定性、方便调节安装，快速、准确的完成加载装置的调整，本发明提供了一种航天器舱体多点起吊静力试验加载装置及方法，具体的技术方案如下。In order to carry out the static test of large-scale cabin lifting, ensure the load-bearing stability of the test loading device, facilitate the adjustment and installation, and quickly and accurately complete the adjustment of the loading device, the invention provides a multi-point lifting static test loading of the spacecraft cabin. Device and method, concrete technical scheme is as follows.
一种航天器舱体多点起吊静力试验加载装置，包括承力地轨、承力支架、斜撑、加载承力梁和加载机构，所述承力地轨上安装有承力支架，承力支架搭建舱体试验空间与舱体结构相配合；所述承力支架包括竖直支撑梁和水平承力梁，承力支架底部安装有斜撑，竖直支撑梁与承力地轨垂直安装，水平承力梁固定在竖直支撑梁上；多个所述加载承力梁固定安装在承力支架的上方，加载承力梁上设置有多个加载安装孔；所述加载机构安装在加载承力梁上。A multi-point hoisting static test loading device for a spacecraft cabin, comprising a load-bearing ground rail, a load-bearing bracket, a diagonal brace, a load-bearing beam and a loading mechanism, the load-bearing ground rail is equipped with a load-bearing bracket, and the bearing The load-bearing bracket builds the cabin test space to match the cabin structure; the load-bearing bracket includes a vertical support beam and a horizontal load-bearing beam. Diagonal braces are installed at the bottom of the load-bearing bracket, and the vertical support beam is vertically installed with the load-bearing ground rail. , the horizontal load-bearing beam is fixed on the vertical support beam; a plurality of the load-bearing beams are fixedly installed above the load-bearing bracket, and a plurality of loading mounting holes are arranged on the load-bearing beam; the loading mechanism is installed on the loading on the bearing beam.
优选的是，加载机构包括第一加载铰链、加载作动器、测力传感器、加载螺杆和第二加载铰链，加载机构通过转接板固定在加载承力梁上。Preferably, the loading mechanism includes a first loading hinge, a loading actuator, a load cell, a loading screw and a second loading hinge, and the loading mechanism is fixed on the loading bearing beam through an adapter plate.
优选的是，转接板和第一加载铰链相连接，加载作动器和第一加载铰链相连接，测力传感器设置在加载作动器和加载螺杆之间，加载螺杆传递加载作动器的作用力，第二加载铰链设置在加载螺杆的端部。Preferably, the adapter plate is connected to the first loading hinge, the loading actuator is connected to the first loading hinge, the load cell is arranged between the loading actuator and the loading screw, and the loading screw transmits the force of the loading actuator. force, the second loading hinge is arranged at the end of the loading screw.
还优选的是，加载承力梁的两端固定在水平承力梁上，水平承力梁上的螺孔与加载承力梁上的螺孔相互配合；多个加载承力梁平行布置。Also preferably, both ends of the load-bearing beam are fixed on the horizontal load-bearing beam, and the screw holes on the horizontal load-bearing beam cooperate with the screw holes on the load-bearing beam; multiple load-bearing beams are arranged in parallel.
还优选的是，承力地轨固定在底面上，多个竖直支撑梁固定安装在承力地轨上，水平承力梁通过螺栓固定安装在竖直支撑梁的上端。Also preferably, the load-bearing ground rail is fixed on the bottom surface, a plurality of vertical support beams are fixedly installed on the load-bearing ground rail, and the horizontal load-bearing beams are fixedly installed on the upper ends of the vertical support beams by bolts.
还优选的是，竖直支撑梁包括多个梯形连接段，每个梯形连接段呈直角梯形，水平承力梁搭设在竖直支撑梁之间。Still preferably, the vertical support beams include a plurality of trapezoidal connecting sections, each trapezoidal connecting section is in the shape of a right-angled trapezoid, and the horizontal load-bearing beams are erected between the vertical supporting beams.
进一步优选的是，梯形连接段的直角边沿同一条直线布置，上一个梯形连接段的长边和下一梯形连接段的短边相连接。Further preferably, the right-angled sides of the trapezoidal connecting segment are arranged along the same straight line, and the long side of the previous trapezoidal connecting segment is connected to the short side of the next trapezoidal connecting segment.
进一步优选的是，竖直支撑梁之间的间距根据航天器舱体结构的尺寸调整，所述加载螺杆的长度根据加载需要调整。Further preferably, the spacing between the vertical support beams is adjusted according to the size of the spacecraft cabin structure, and the length of the loading screw is adjusted according to loading requirements.
一种航天器舱体多点起吊静力试验加载方法，利用上述的一种航天器舱体多点起吊静力试验加载装置，其特征在于，步骤包括：确定舱体结构的起吊接口位置，安装航天器舱体多点起吊静力试验加载装置，根据起吊接口的数量和位置确定加载机构的安装数量和位置，通过加载铰链调整加载角度施加横向、纵向载荷，进行起吊静力试验，考核各个吊接口的稳定性。 A loading method for a multi-point hoisting static test of a spacecraft cabin, using the above-mentioned multi-point hoisting static test loading device for a spacecraft cabin, characterized in that the steps include: determining the position of the hoisting interface of the cabin structure, installing The multi-point hoisting static test loading device of the spacecraft cabin, the installation quantity and position of the loading mechanism are determined according to the number and position of the hoisting interface, and the horizontal and longitudinal loads are applied by adjusting the loading angle through the loading hinge, and the hoisting static test is carried out. interface stability.
进一步优选的是，测力传感器监测载荷的大小，加载作动器调整载荷施加的大小；所述载荷的大小和方向根据舱体起吊、运输实际吊装情况确定。Further preferably, the load cell monitors the magnitude of the load, and the loading actuator adjusts the magnitude of the applied load; the magnitude and direction of the load are determined according to the actual hoisting conditions of the cabin body lifting and transportation.
本发明提供的一种航天器舱体多点起吊静力试验加载装置及方法有益效果包括：利用承力支架的试验装置结构可以进行多个加载位置、多种量级横向和纵向载荷的试验，保证了大型舱体的考核更加符合实际；加载装置采用转接板和螺栓连接，该种固定方式安装拆解方便，并且转接板和加载承力梁相互配合，调节快速，安装精准，提高了试验效率；该加载装置能够实现舱体大跨距加载点的加载，并且承载能力强；加载作动器通过配置铰链结构，方便了加载角度的调整，进而可以模拟大型舱体不同阶段的起吊、运输情况。The beneficial effects of the multi-point hoisting static test loading device and method of a spacecraft cabin body provided by the present invention include: the test device structure of the load-bearing support can be used to perform tests on multiple loading positions and various magnitudes of lateral and longitudinal loads, It ensures that the assessment of large cabins is more realistic; the loading device is connected by an adapter plate and bolts. Test efficiency; the loading device can realize the loading of the large-span loading point of the cabin, and has a strong bearing capacity; the loading actuator is equipped with a hinge structure, which facilitates the adjustment of the loading angle, and can simulate the lifting of the large cabin at different stages. Shipping condition.
图1是航天器舱体多点起吊静力试验加载装置结构示意图；Fig. 1 is a schematic diagram of the structure of the multi-point hoisting static test loading device of the spacecraft cabin;
图2是承力支架部分结构示意图；Fig. 2 is a schematic diagram of the partial structure of the bearing bracket;
图3是加载承力梁和加载机构的结构示意图；Fig. 3 is a schematic structural view of a loading beam and a loading mechanism;
图4是加载机构的结构示意图；Fig. 4 is the structural representation of loading mechanism;
图5是试验舱体试验机构示意图；Fig. 5 is a schematic diagram of the test mechanism of the test cabin;
图6是吊接口的连接示意图；Fig. 6 is the connection schematic diagram of hanging interface;
图中：1-承力地轨，2-承力支架，3-斜撑，4-加载承力梁，5-加载机构，6-转接板，7-舱体结构，8-吊接口；In the figure: 1-load-bearing ground rail, 2-load-bearing bracket, 3-slant brace, 4-loading load-bearing beam, 5-loading mechanism, 6-transfer plate, 7-cabin structure, 8-hanging interface;
21-竖直支撑梁，22-水平承力梁；21-vertical support beam, 22-horizontal bearing beam;
51-第一加载铰链，52-加载作动器，53-测力传感器，54-加载螺杆，55-第二加载铰链。51 - the first loading hinge, 52 - the loading actuator, 53 - the load cell, 54 - the loading screw, 55 - the second loading hinge.
结合图1至图6所示，对本发明提供的一种航天器舱体多点起吊静力试验加载装置及方法的具体实施方式进行说明。With reference to FIGS. 1 to 6 , the specific implementation of a multi-point hoisting static test loading device and method for a spacecraft cabin provided by the present invention will be described.
一种航天器舱体多点起吊静力试验加载装置，包括承力地轨1、承力支架2、斜撑3、加载承力梁4和加载机构5。承力地轨1在底面上支撑并可以调整装置整体的水平，承力支架2用于搭建试验空间并支撑试验舱体结构，为加载承力梁的安装提供便利，加载承力梁4确定多个加载机构的安装点，从而灵活的确定试验加载方案；加载机构5用于施加载荷，并且可以灵活的调整加载方向，模拟大型舱体不同阶段的起吊、运输情况。A multi-point hoisting static test loading device for a spacecraft cabin includes a load-bearing ground rail 1, a load-bearing bracket 2, a diagonal brace 3, a load-bearing beam 4, and a loading mechanism 5. The load-bearing ground rail 1 is supported on the bottom surface and can adjust the overall level of the device. The load-bearing bracket 2 is used to build the test space and support the structure of the test cabin, which provides convenience for the installation of the load-bearing beam. The load-bearing beam 4 determines how many There are three installation points of the loading mechanism, so as to flexibly determine the test loading scheme; the loading mechanism 5 is used to apply the load, and the loading direction can be flexibly adjusted to simulate the lifting and transportation conditions of the large cabin at different stages.
其中，承力地轨1可以直接固定在地面上，承力地轨1厚度较大，并且承力地轨1的上表面平整；承力地轨1还上还可设置有与承力支架相互配合的卡槽，使承力支架2方便的压接在承力地轨上。承力地轨1上安装有承力支架，承力支架2搭建舱体试验空间与舱体结构7相配合，承力支架2能够支撑大载荷的施加，并且方便的放置大型舱体结构；常规的大型支撑结构通常为一体式结构，由于需要进行多种尺寸、多种型号试验舱体结构试验，因此采用承力梁直接的搭建形式，方便安装调整，在保证支架结构稳定性的同时还保证了其灵活性。承力支架2包括竖直支撑梁21和水平承力梁22，承力支架2底部安装有斜撑，斜撑3对承力支架进行加固，进一步保证了支架结构的稳定性。竖直支撑梁与承力地轨垂直安装，从而可以为载荷的施加方向提供参照，水平承力梁22固定在竖直支撑梁上，为加载承力梁的安装提供方便，并且可以提升结构整体的稳定性。多个加载承力梁固定安装在承力支架的上方，加载承力梁上设置有多个加载安装孔，方便加载机构的安装调整，加载机构安装在加载承力梁上，加载机构可以模拟大型舱体吊接口在吊装时的受力情况。Wherein, the load-bearing ground rail 1 can be directly fixed on the ground, and the load-bearing ground rail 1 has a relatively large thickness, and the upper surface of the load-bearing ground rail 1 is flat; The matching card slot makes the load-bearing bracket 2 conveniently crimped on the load-bearing ground rail. A load-bearing bracket is installed on the load-bearing ground rail 1, and the load-bearing bracket 2 builds a cabin test space to cooperate with the cabin structure 7. The load-bearing bracket 2 can support the application of a large load, and it is convenient to place a large cabin structure; The large-scale support structure is usually a one-piece structure. Since various sizes and types of test cabin structure tests are required, the direct construction of the load-bearing beam is used to facilitate installation and adjustment. It ensures the stability of the support structure while also ensuring its flexibility. The load-bearing support 2 includes a vertical support beam 21 and a horizontal load-bearing beam 22. The bottom of the load-bearing support 2 is equipped with a diagonal brace, and the diagonal brace 3 reinforces the load-bearing support, further ensuring the stability of the support structure. The vertical support beam and the load-bearing ground rail are installed vertically, so as to provide a reference for the direction of load application. The horizontal load-bearing beam 22 is fixed on the vertical support beam, which provides convenience for the installation of the load-bearing beam and can improve the overall structure. stability. Multiple load-bearing beams are fixedly installed above the load-bearing bracket. Multiple loading mounting holes are provided on the load-bearing beam to facilitate the installation and adjustment of the loading mechanism. The loading mechanism is installed on the load-bearing beam, and the loading mechanism can simulate large-scale The stress situation of the crane interface of the cabin body during hoisting.
加载机构5包括第一加载铰链51、加载作动器52、测力传感器53、加载螺杆54和第二加载铰链55，加载机构5通过转接板固定在加载承力梁上，加载作动器52施加载荷，两个加载铰链51相互配合调整加载方向。转接板和第一加载铰链51相连接，加载作动器52和第一加载铰链51相连接，测力传感器53设置在加载作动器和加载螺杆之间，监测施加载荷的大小，加载螺杆54传递加载作动器的作用力，第二加载铰链55设置在加载螺杆的端部，并且可以和舱体结构7的起吊接口8相连接，完成大型舱体的考核。The loading mechanism 5 comprises a first loading hinge 51, a loading actuator 52, a load cell 53, a loading screw 54 and a second loading hinge 55, the loading mechanism 5 is fixed on the loading bearing beam through an adapter plate, and the loading actuator 52 to apply load, and the two loading hinges 51 cooperate with each other to adjust the loading direction. The adapter plate is connected with the first loading hinge 51, the loading actuator 52 is connected with the first loading hinge 51, and the load cell 53 is arranged between the loading actuator and the loading screw to monitor the magnitude of the applied load, and the loading screw 54 transmits the active force of the loading actuator, and the second loading hinge 55 is arranged at the end of the loading screw, and can be connected with the lifting interface 8 of the cabin structure 7 to complete the assessment of the large cabin.
加载承力梁4的两端固定在水平承力梁22上，多个加载承力梁4可以平行布置，加载承力梁4之间的间隔根据加载需要确定，可以通过螺纹连接从而方便拆卸，水平承力梁22上的螺孔与加载承力梁上的螺孔相互配合。其中承力梁的螺孔为竖直方向上的通孔，从而方便加载机构的安装，灵活的施加载荷。The two ends of the load-bearing beam 4 are fixed on the horizontal load-bearing beam 22, and a plurality of load-bearing beams 4 can be arranged in parallel, and the interval between the load-bearing beams 4 is determined according to the loading requirements, and can be easily disassembled by threaded connection. The screw holes on the horizontal bearing beam 22 cooperate with the screw holes on the loading bearing beam. The screw holes of the load-bearing beam are through holes in the vertical direction, so as to facilitate the installation of the loading mechanism and flexibly apply the load.
承力地轨1固定在底面上，承力地轨1的尺寸一般大于试验的舱体结构尺寸，多个竖直支撑梁固定安装在承力地轨上，水平承力梁22通过螺栓固定安装在竖直支撑梁21的上端。本实施例中设置了4个相同的竖直支撑梁21，两两一组，两组竖直支撑梁21之间的跨度较大，每组竖直支撑梁之间的间距较小；每组竖直支撑梁21之间平行。竖直支撑梁21包括多个梯形连接段，每个梯形连接段呈直角梯形，水平承力梁搭设在竖直支撑梁之间。梯形连接段的直角边沿同一条直线布置，上一个梯形连接段的长边和下一梯形连接段的短边相连接，经现场验证该结构的连接方式可以满足试验的稳定性、安全性等需求，并且安装简便，试验效率更高。本实施例中同一条直线上的梯形边在承力支架的内侧，梯形的斜边朝向承力支架的外侧，进一步的保证了承力支架的稳定性，同时还方便了舱体结构的放置。根据试验舱体结构7的尺寸可以快速的搭建承力支架2，试验舱体结构7在竖直支撑梁之间，该承力支架2具有安装灵活方便，稳定性高等优点。The load-bearing ground rail 1 is fixed on the bottom surface, and the size of the load-bearing ground rail 1 is generally larger than the test cabin structure size. Multiple vertical support beams are fixedly installed on the load-bearing ground rail, and the horizontal load-bearing beams 22 are fixed and installed by bolts. At the upper end of the vertical support beam 21. 4 identical vertical support beams 21 are set in the present embodiment, two by two groups, the span between two groups of vertical support beams 21 is larger, and the spacing between each group of vertical support beams is smaller; The vertical support beams 21 are parallel to each other. The vertical support beams 21 include a plurality of trapezoidal connecting sections, each trapezoidal connecting section is in the shape of a right-angled trapezoid, and the horizontal load-bearing beams are erected between the vertical supporting beams. The right-angled edges of the trapezoidal connecting section are arranged on the same straight line, and the long side of the previous trapezoidal connecting section is connected with the short side of the next trapezoidal connecting section. It has been verified on site that the connection method of this structure can meet the stability and safety requirements of the test. , and the installation is simple and the test efficiency is higher. In this embodiment, the side of the trapezoid on the same straight line is inside the load-bearing bracket, and the hypotenuse of the trapezoid faces the outside of the load-bearing bracket, which further ensures the stability of the load-bearing bracket and facilitates the placement of the cabin structure. According to the size of the test cabin structure 7, the load-bearing support 2 can be quickly built. The test cabin structure 7 is between the vertical support beams. The load-bearing support 2 has the advantages of flexible and convenient installation and high stability.
竖直支撑梁21之间的间距根据航天器舱体结构的尺寸调整，其中舱体结构7的尺寸与航天器实际舱体结构的尺寸相同，舱体结构7一般呈圆柱形，通常直径大于4m，高度大于直径，普通的加载试验装置不能实现大跨度的加载。针对航天器大型舱段的对接需求，对接过程中需要进行舱段位姿调整，验证位姿调整过程中各个吊装点的综合受力是否满足舱段对接的需求，原有的静力试验方法费事费力，已经难以满足多个吊点，多个加载方向的试验需求。其中加载螺杆54的长度可以根据加载需要调整，从而满足种型号舱体结构的试验需求。The spacing between the vertical support beams 21 is adjusted according to the size of the spacecraft cabin structure, wherein the size of the cabin structure 7 is the same as the size of the actual cabin structure of the spacecraft, and the cabin structure 7 is generally cylindrical, usually with a diameter greater than 4m , the height is greater than the diameter, and the ordinary loading test device cannot realize large-span loading. In view of the docking requirements of the large-scale spacecraft cabin, the cabin pose needs to be adjusted during the docking process to verify whether the comprehensive force of each hoisting point during the pose adjustment process meets the requirements of the cabin docking. The original static test method is time-consuming and laborious. , it has been difficult to meet the test requirements of multiple lifting points and multiple loading directions. The length of the loading screw 54 can be adjusted according to loading requirements, so as to meet the test requirements of various types of cabin structures.
一种航天器舱体多点起吊静力试验加载方法，利用上述的一种航天器舱体多点起吊静力试验加载装置，其步骤包括：确定舱体结构的起吊接口位置，包括吊接口的连接方式、吊接口在舱体上的相对位置，以及吊接口的尺寸、吊接口可能的受力情况；安装航天器舱体多点起吊静力试验加载装置，具体包括先在承力地轨上压接安装承力支架、斜撑，随后螺钉连接加载承力梁和加载机构；根据起吊接口的数量和位置确定加载机构的安装数量和位置，各个加载机构与吊接口相互配合对应。试验时通过加载铰链调整加载角度施加横向、纵向载荷，进行起吊静力试验，考核各个吊接口的稳定性。A loading method for a multi-point hoisting static test of a spacecraft cabin, using the above-mentioned multi-point hoisting static test loading device for a spacecraft cabin, the steps include: determining the position of the hoisting interface of the cabin structure, including the position of the hoisting interface The connection method, the relative position of the hoisting interface on the cabin body, the size of the hoisting interface, and the possible force of the hoisting interface; the installation of a multi-point hoisting static test loading device for the spacecraft cabin, including first placing the load on the load-bearing ground rail. The load-bearing brackets and braces are installed by crimping, and then the load-bearing beam and the loading mechanism are connected by screws; the number and position of the loading mechanism are determined according to the number and position of the lifting interface, and each loading mechanism and the lifting interface cooperate with each other. During the test, the lateral and longitudinal loads are applied by adjusting the loading angle of the loading hinge, and the lifting static test is carried out to assess the stability of each lifting interface.
其中，试验时横向载荷和纵向载荷经过计算后以合力的形式通过铰链周向运动以合力的形式模拟，通过调整螺杆长度及铰链与产品起吊点连接调整加载。Among them, the lateral load and longitudinal load during the test are calculated and simulated in the form of resultant force through the circumferential movement of the hinge, and the load is adjusted by adjusting the length of the screw and the connection between the hinge and the lifting point of the product.
试验加载装置的安装过程具体包括：在承力地轨上压接竖直支撑梁，在竖直支撑梁侧面安装斜撑，保证稳定性，竖直支撑梁上面螺接水平承力梁，完成承力支架的搭建；在承力支架上通过固定螺栓螺接加载承力梁；在加载位置依次安装转接板、第一加载铰链、销钉、加载作动器、测力传感器、加载螺杆、第二加载铰链，完成加载机构的安装；通过上述安装可实现航天器舱体结构多点起吊静力试验的加载实施。The installation process of the test loading device specifically includes: crimping the vertical support beam on the load-bearing ground rail, installing diagonal braces on the side of the vertical support beam to ensure stability, and screwing the horizontal load-bearing beam on the vertical support beam to complete the bearing. The construction of the force support; the load-bearing beam is screwed on the load-bearing support by fixing bolts; the adapter plate, the first loading hinge, the pin, the loading actuator, the load cell, the loading screw, and the second load are installed in sequence at the loading position. Load the hinge to complete the installation of the loading mechanism; through the above installation, the loading implementation of the multi-point hoisting static test of the spacecraft cabin structure can be realized.
试验时还可以通过测力传感器监测载荷的大小，加载作动器调整载荷施加的大小，从而达到试验的目的。载荷的大小和方向根据舱体起吊、运输实际吊装情况确定。试验完成后可以快速的拆解加载装置，根据试验方案重新布置，另外由于承力支架建立了横向和纵向的坐标体系，从而可以提高安装精度。同时进行多个吊点的测试，可以大大的提高试验效率。During the test, the magnitude of the load can also be monitored by the load cell, and the actuator can be loaded to adjust the magnitude of the load, so as to achieve the purpose of the test. The size and direction of the load are determined according to the actual hoisting conditions of the cabin body lifting and transportation. After the test is completed, the loading device can be quickly disassembled and rearranged according to the test plan. In addition, since the load-bearing bracket has established a horizontal and vertical coordinate system, the installation accuracy can be improved. Simultaneous testing of multiple lifting points can greatly improve test efficiency.
航天器舱体多点起吊静力试验加载装置及方法，利用承力支架的试验装置结构可以进行多个加载位置、多种量级横向和纵向载荷的试验，保证了大型舱体的考核更加符合实际；加载装置采用转接板和螺栓连接，该种固定方式安装拆解方便，并且转接板和加载承力梁相互配合，调节快速，安装精准，提高了试验效率；该加载装置能够实现舱体大跨距加载点的加载，并且承载能力强；加载作动器通过配置铰链结构，方便了加载角度的调整，进而可以模拟大型舱体不同阶段的起吊、运输情况。The multi-point hoisting static test loading device and method of the spacecraft cabin, using the test device structure of the load-bearing bracket, can carry out tests of multiple loading positions and various magnitudes of lateral and longitudinal loads, ensuring that the assessment of large cabins is more in line with Actually; the loading device is connected by an adapter plate and bolts, which is easy to install and disassemble, and the adapter plate and the load-bearing beam cooperate with each other, the adjustment is fast, the installation is accurate, and the test efficiency is improved; the loading device can realize the cabin The loading point of the large-span loading point has a strong bearing capacity; the loading actuator is equipped with a hinge structure, which facilitates the adjustment of the loading angle, and then can simulate the lifting and transportation of large cabins at different stages.
当然，上述说明并非是对本发明的限制，本发明也并不仅限于上述举例，本技术领域的技术人员在本发明的实质范围内所做出的变化、改型、添加或替换，也应属于本发明的保护范围。Of course, the above descriptions are not intended to limit the present invention, and the present invention is not limited to the above examples. Changes, modifications, additions or replacements made by those skilled in the art within the scope of the present invention shall also belong to the present invention. protection scope of the invention.
Claims (10)
- 一种航天器舱体多点起吊静力试验加载装置，其特征在于，包括承力地轨、承力支架、斜撑、加载承力梁和加载机构，所述承力地轨上安装有承力支架，承力支架搭建舱体试验空间与舱体结构相配合；所述承力支架包括竖直支撑梁和水平承力梁，承力支架底部安装有斜撑，竖直支撑梁与承力地轨垂直安装，水平承力梁固定在竖直支撑梁上；多个所述加载承力梁固定安装在承力支架的上方，加载承力梁上设置有多个加载安装孔；所述加载机构安装在加载承力梁上。A multi-point hoisting static test loading device for a spacecraft cabin is characterized in that it includes a load-bearing ground rail, a load-bearing bracket, a diagonal brace, a loading load-bearing beam and a loading mechanism, and a load-bearing ground rail is installed on the load-bearing ground rail. The load-bearing bracket, the load-bearing bracket builds the cabin test space to match the cabin structure; the load-bearing bracket includes a vertical support beam and a horizontal load-bearing beam, and a diagonal brace is installed at the bottom of the load-bearing bracket, and the vertical support beam and the load-bearing The ground rail is installed vertically, and the horizontal load-bearing beam is fixed on the vertical support beam; a plurality of the load-bearing beams are fixedly installed above the load-bearing bracket, and a plurality of loading installation holes are arranged on the load-bearing beam; The mechanism is mounted on a load bearing beam.
- 根据权利要求1所述的一种航天器舱体多点起吊静力试验加载装置，其特征在于，所述加载机构包括第一加载铰链、加载作动器、测力传感器、加载螺杆和第二加载铰链，加载机构通过转接板固定在加载承力梁上。The multi-point hoisting static test loading device for spacecraft cabin according to claim 1, wherein the loading mechanism comprises a first loading hinge, a loading actuator, a load cell, a loading screw and a second The loading hinge, the loading mechanism is fixed on the loading bearing beam through the adapter plate.
- 根据权利要求2所述的一种航天器舱体多点起吊静力试验加载装置，其特征在于，所述转接板和第一加载铰链相连接，加载作动器和第一加载铰链相连接，测力传感器设置在加载作动器和加载螺杆之间，加载螺杆传递加载作动器的作用力，第二加载铰链设置在加载螺杆的端部。The multi-point hoisting static test loading device for a spacecraft cabin according to claim 2, wherein the adapter plate is connected to the first loading hinge, and the loading actuator is connected to the first loading hinge , the load cell is arranged between the loading actuator and the loading screw, the loading screw transmits the force of the loading actuator, and the second loading hinge is arranged at the end of the loading screw.
- 根据权利要求1或3所述的一种航天器舱体多点起吊静力试验加载装置，其特征在于，所述加载承力梁的两端固定在水平承力梁上，水平承力梁上的螺孔与加载承力梁上的螺孔相互配合；多个加载承力梁平行布置。The multi-point hoisting static test loading device for spacecraft cabin according to claim 1 or 3, characterized in that, the two ends of the load-bearing beam are fixed on the horizontal load-bearing beam, and the horizontal load-bearing beam The screw holes on the load-bearing beam cooperate with the screw holes on the load-bearing beam; multiple load-bearing beams are arranged in parallel.
- 根据权利要求1所述的一种航天器舱体多点起吊静力试验加载装置，其特征在于，所述承力地轨固定在底面上，多个竖直支撑梁固定安装在承力地轨上，水平承力梁通过螺栓固定安装在竖直支撑梁的上端。The multi-point hoisting static test loading device for a spacecraft cabin according to claim 1, wherein the load-bearing ground rail is fixed on the bottom surface, and a plurality of vertical support beams are fixedly installed on the load-bearing ground rail Above, the horizontal load-bearing beam is fixedly installed on the upper end of the vertical support beam by bolts.
- 根据权利要求5所述的一种航天器舱体多点起吊静力试验加载装置，其特征在于，所述竖直支撑梁包括多个梯形连接段，每个梯形连接段呈直角梯形，水平承力梁搭设在竖直支撑梁之间。The multi-point hoisting static test loading device for a spacecraft cabin according to claim 5, wherein the vertical support beam includes a plurality of trapezoidal connecting sections, each trapezoidal connecting section is a right-angled trapezoid, and the horizontal bearing The force beams are erected between the vertical support beams.
- 根据权利要求6所述的一种航天器舱体多点起吊静力试验加载装置，其特征在于，所述梯形连接段的直角边沿同一条直线布置，上一个梯形连接段的长边和下一梯形连接段的短边相连接。The multi-point hoisting static test loading device for a spacecraft cabin according to claim 6, wherein the right-angled edges of the trapezoidal connecting section are arranged along the same straight line, and the long side of the previous trapezoidal connecting section and the next The short sides of the trapezoidal connecting segments are connected.
- 根据权利要求1所述的一种航天器舱体多点起吊静力试验加载装置，其特征在于，所述竖直支撑梁之间的间距根据航天器舱体结构的尺寸调整，所述加载螺杆的长度根据加载需要调整。The multi-point hoisting static test loading device for a spacecraft cabin according to claim 1, wherein the spacing between the vertical support beams is adjusted according to the size of the spacecraft cabin structure, and the loading screw The length is adjusted according to loading needs.
- 一种航天器舱体多点起吊静力试验加载方法，利用权利要求1至8任一项所述的一种航天器舱体多点起吊静力试验加载装置，其特征在于，步骤包括：确定舱体结构的起吊接口位置，安装航天器舱体多点起吊静力试验加载装置，根据起吊接口的数量和位置确定加载机构的安装数量和位置，通过加载铰链调整加载角度施加横向、纵向载荷，进行起吊静力试验，考核各个吊接口的稳定性。A loading method for a multi-point hoisting static test of a spacecraft cabin, using the multi-point hoisting static test loading device for a spacecraft cabin according to any one of claims 1 to 8, characterized in that the steps include: determining For the position of the lifting interface of the cabin structure, install the multi-point lifting static test loading device of the spacecraft cabin, determine the number and position of the loading mechanism according to the number and position of the lifting interface, adjust the loading angle through the loading hinge to apply lateral and longitudinal loads, Carry out a lifting static test to assess the stability of each lifting interface.
- 根据权利要求9所述的一种航天器舱体多点起吊静力试验加载方法，其特征在于，所述测力传感器监测载荷的大小，加载作动器调整载荷施加的大小；所述载荷的大小和方向根据舱体起吊、运输实际吊装情况确定。The multi-point hoisting static test loading method of a spacecraft cabin according to claim 9, wherein the load cell monitors the size of the load, and the loading actuator adjusts the applied size of the load; The size and direction are determined according to the actual hoisting conditions of the cabin body hoisting and transportation.
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- 2021-12-31 CN CN202111661674.2A patent/CN114476147B/en active Active
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2022
- 2022-04-11 WO PCT/CN2022/086025 patent/WO2023123732A1/en unknown
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5600104A (en) * | 1993-10-20 | 1997-02-04 | Structural Instrumentation, Inc. | Load cell having reduced sensitivity to non-symmetrical beam loading |
| JP2006184026A (en) * | 2004-12-24 | 2006-07-13 | Takenaka Komuten Co Ltd | Applied force testing machine |
| CN104034549A (en) * | 2014-06-24 | 2014-09-10 | 中国飞机强度研究所 | Loading device for aircraft wing large deformation tests |
| CN209014390U (en) * | 2018-09-19 | 2019-06-21 | 中国地震局工程力学研究所 | Static loading test device |
| CN112478192A (en) * | 2020-10-30 | 2021-03-12 | 中国直升机设计研究所 | Full-mechanical static test loading rack of small-load helicopter |
| CN113335560A (en) * | 2021-06-04 | 2021-09-03 | 中国飞机强度研究所 | Complicated load box section or barrel section testing device and method |
| CN114476147A (en) * | 2021-12-31 | 2022-05-13 | 北京空间机电研究所 | Spacecraft cabin multi-point hoisting static test loading device and method |
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| Publication number | Publication date |
|---|---|
| CN114476147B (en) | 2022-11-01 |
| CN114476147A (en) | 2022-05-13 |
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